流量可调燃气发生器压强控制仿真
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摘要
为了提高流量可调燃气发生器的流量控制效果,建立了燃气发生器流量调节系统动态模型。针对燃气发生器流量调节系统时变性的特点,引入了一种基于神经网络PI(比例积分)算法的压强控制系统;研究了不同自由容积条件下神经网络PI控制系统与PI控制系统控制效果的有效性,得到了控制器的压强工作范围。不同自由容积条件下的2种算法的仿真结果表明:基于神经网络PI算法的压强控制系统响应速度较快,压力超调量较小,压强工作范围大,系统的动态特性较好,能更好地解决燃气发生器流量调节系统时变性带来的控制精度差的问题。
In order to improve the control effect of adjustable flow gas generator,a dynamic model for the adjustable-flow gas generator was built. According to the time-varying characteristics of the gas generator system,a pressure control system based on neural network PI( proportional plus integral) algorithm was designed.The control accuracy of neural networks PI algorithm and PI algorithm were studied under the conditions of different free-volume,and the pressure operating range of two controllers were obtained. The results under different working-conditions show that the pressure control system based on neural network PI algorithm has faster response speed,less pressure overshoot,wider pressure operating range and better dynamic characteristics,so the control problems caused by time-varying characteristics of the adjustableflow gas generator system can be solved effectively.
In order to improve the control effect of adjustable flow gas generator,a dynamic model for the adjustable-flow gas generator was built. According to the time-varying characteristics of the gas generator system,a pressure control system based on neural network PI( proportional plus integral) algorithm was designed.The control accuracy of neural networks PI algorithm and PI algorithm were studied under the conditions of different free-volume,and the pressure operating range of two controllers were obtained. The results under different working-conditions show that the pressure control system based on neural network PI algorithm has faster response speed,less pressure overshoot,wider pressure operating range and better dynamic characteristics,so the control problems caused by time-varying characteristics of the adjustableflow gas generator system can be solved effectively.
引文
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[2]CHANG J,LI B,BAO W,et al.Thrust control system design of ducted rockets[J].Acta Astronautica,2011,69(1/2):86-95.
[3]WILSON R,LIMAGE C,HEWITT P.The evolution of ramjet missile propulsion in the U.S.and where we are headed:AIAA A96-37261[R].Reston,VA:AIAA,1996.
[4]NAKAYAMA H,IKEGAMI Y,YOSHIDA A,et al.Full-scale firing tests of variable flow ducted rocket engines employing gap solid fuel gas generator:AIAA-2009-5121[R].Reston,VA:AIAA,2009.
[5]LV X,NIU W,YU D,et al.Controlled parameter selection in solid ducted ramjet for thrust control:AIAA-2009-5122[R].Reston,VA:AIAA,2009.
[6]马立坤.燃气流量可调固体火箭冲压发动机动态响应过程研究[D].长沙:国防科学技术大学,2011.MA Li-kun.Investigation of the response process of variable flow ducted rocket[D].Changsha:National University of Defense Technology,2011.(in Chinese)
[7]BESSER H.History of ducted rocket development at bayernchemie:AIAA-2008-5261[R].Reston,VA:AIAA,2008.
[8]鲍文,牛文玉,陈林泉,等.固体火箭冲压发动机燃气流量调节特性[J].推进技术,2007,28(4):433-436.BAO Wen,NIU Wen-yu,CHEN Lin-quan,et al.Regulating property of the flow in a solid ducted rocket[J].Journal of Propulsion Technology,2007,28(4):433-436.(in Chinese)
[9]NIU W Y,BAO W,CHANG J,et al.Control system design and experiment of needle-type gas regulating system for ducted rocket[J].Journal of Aerospace Engineering,2010,224(5):563-573.
[10]周俊,周长省,陈雄.基于BP神经网络固冲发动机燃气流量调节控制[J].计算机仿真,2015,32(1):56-59.ZHOU Jun,ZHOU Chang-sheng,CHEN Xiong.GA-BP neural network control for ducted rocket gas regulating system[J].Computer Simulation,2015,32(1):56-59.(in Chinese)
[11]聂聆聪,刘志明,刘源祥.流量可调燃气发生器压力闭环模糊控制算法[J].推进技术,2013,34(4):551-556.NIE Ling-cong,LIU Zhi-ming,LIU Yuan-xiang.Pressure close loop fuzzy control method of a flow adjustable gas generator[J].Journal of Propulsion Technology,2013,34(4):551-556.(in Chinese)
[12]刘源翔,聂聆聪,张皎,等.基于线性自抗扰控制器的燃气流量可调发生器压强控制算法研究[J].推进技术,2015,36(12):1 768-1 773.LIU Yuan-xiang,NIE Ling-cong,ZHANG Jiao,et al.Research on pressure control algorithm of a flow adjustable gas generator based on linear active disturbance rejection control[J].Journal of P ropulsion Technology,2015,36(12):1 768-1 773.(in Chinese)
[13]刘源翔.变流量整体式固冲发动机控制系统研究[D].北京:北京理工大学,2015.LIU Yuan-xiang.Study on control system of the throtteanble ducted rocket[D].Beijing:Beijing Institute of Technology,2015.(in Chinese)
[14]LEE J,KO H.A study on the performance characteristics of blunt body pintle nozzle:AIAN-2013-4080[R].Reston,VA:AIAA,2013.
[15]唐金兰.固体火箭发动机原理[M].北京:国防工业出版社,2013.TANG Jin-lan.Principle of solid rocket motor[M].Beijing:National Defence Industry Press,2013.(in Chinese)